CA2851891A1 - Thrust reverser having twin doors - Google Patents

Abstract

This thrust reverser for an aircraft turbojet engine nacelle comprises: at least one pair of twin doors comprising an upstream door (7), a downstream door (9) connected by at least one connecting rod (45a, 45b) to the door upstream (7), and at least one actuating cylinder (43) of the upstream door (7), between a "direct jet" position in which these two doors are closed, and an "inverted jet" position in which these two doors are open and able to deflect at least a part of the cold air flow likely to circulate inside the nacelle, and means (25) for locking / unlocking said upstream and downstream doors between them under the only one action of said cylinder (43).

Description

Twin door thrust reverser This patent application relates to an inverter of thrust with twin doors.
It is known from the prior art, and in particular from patent application FR2754565, a thrust reverser with twin doors, each pair of twin doors including an upstream door and a door downstream.
Such a thrust reverser allows a large air leakage flow rate cold circulating inside the nacelle, and therefore a braking all the more effective landing of the aircraft.
In such a thrust reverser, there must be a certain amount of number of locks providing redundancy to remove any risk inadvertent opening of the doors.
More precisely, to respect the safety rules in force, three independent locking systems must be provided for each upstream and downstream door of each pair of twin doors.
A first locking system comprises a solidarity lock of the front frame of the thrust reverser, and cooperating with the upstream door of the pair of twin doors.
The downstream door being connected by a pair of connecting rods to the upstream door, this first locking system also ensures the locking of the door downstream.
A second locking system comprises a system of synchronization of the opening of adjacent doors, such as that disclosed by patent application FR2823259: such a system makes it possible to prevent the opening of an upstream door (and therefore of its associated downstream door) as long as adjacent upstream door is not itself open.
A third locking system cooperates directly with the actuating cylinder of the upstream door.
In such an arrangement, there are therefore two locking systems ordered by pair of twin door: the first and third systems aforementioned; only the second locking system is passive, and therefore requires no control means.
Thus, for a twin-door thrust reverser comprising typically four pairs of twin doors, 8 locks must be provided

2 ordered, which is cumbersome, complex and costly for both installation and maintenance.
The present invention is thus particularly intended to provide a simplification of the locking means of such a thrust reverser.
This object of the invention is achieved with a thrust reverser for aircraft turbojet engine nacelle, comprising:
at least one pair of twin doors comprising a door upstream, a downstream door connected by at least one connecting rod to the upstream door, and at least one actuating cylinder of the upstream door, between a direct jet position in which these two doors are closed, and a reverse jet position in which these two doors are open and able to deflect at least part of the cold airflow likely to flow to inside the basket, this thrust reverser being remarkable in that it comprises means for locking / unlocking said upstream and downstream gates between they under the sole action of said cylinder.
The locking of the upstream and downstream doors between them constitutes a interlocking system independent of the first and second mentioned above, thus requiring no means of control specific because they are the only movements of the cylinder at the opening and the closing the doors that allow to realize their locking / unlocking.
This gives three independent locking systems for the pair of twin doors, including only one lock ordered:
that of the first locking system mentioned above.
Thus, for a thrust reverser comprising four pairs of twin doors, only four locks ordered are required, which simplifies and simplifies costs and reduces costs.
made considerable.
According to other optional features of the inverter of thrust according to the invention:
said locking / unlocking means comprise:
a hook pivotally mounted on said upstream door, between a locking position of a pawn secured to said door downstream, and an unlock position of this counter, - Elastic return means of said hook to its position locking,

3 a latch pivotally mounted on said upstream door between a locking position in which it holds said hook in its locking position, and a position of unlocking, in which it authorizes the passage of said hook from its locking position to its unlocking position, - Elastic return means of said latch to its position blocking, said jack and said latch being arranged relative to one another so that an extension of said jack rotates said latch towards its unlocking position;
said hook and said latch are pivotally mounted around axes substantially perpendicular to the axes of rotation of the upstream and downstream gates and at the axis of the nacelle;
said hook and said latch are pivotally mounted around axes substantially parallel to the axes of rotation of the upstream and downstream doors;
said hook is pivotally mounted about an axis substantially parallel to the axis of the nacelle, and said latch is pivotally mounted around of an axis substantially perpendicular to the axes of rotation of the upstream and downstream gates and at the axis of the nacelle;
said locking / unlocking means comprise:
a bolt slidably mounted in said upstream door, between a locking position of a strike formed in said door downstream, and an unlock position of this striker, - Elastic return means of said bolt to its position of locking, a latch pivotally mounted on said upstream and cooperating door with said bolt so that a rotation of this latch has to effect of sliding this bolt, said jack and said latch being arranged relative to one another so that an extension of said cylinder rotates said trigger in a direction causing the sliding of said bolt towards its unlocking position;
said locking / unlocking means comprise in in addition to a stirrup pivotally mounted on said upstream door about an axis substantially parallel to the axes of rotation of said upstream and downstream gates, and WO 2013/06866

4 PCT / FR2012 / 052409 elastic means recalling this stirrup to a position in which it maintains said bolt in its unlocked position;
said downstream door comprises a support member, able to rotate said yoke against said resilient means.
said locking / unlocking means comprise:
a hook pivotally mounted on said downstream door, between a locking position of a pawn secured to the fixed structure said inverter, and an unlocking position of this pin, - Elastic return means of said hook to its position locking, a latch pivotally mounted on said downstream door between a locking position in which it holds said hook in its locking position, and a position of unlocking, in which it authorizes the passage of said hook from its locking position to its unlocking position, - Elastic return means of said latch to its position blocking, - a cable whose end is slidably mounted on said upstream door, and whose other end is connected to said latch, so that an extension of said jack causes the sliding said cable with respect to said upstream door, and and rotation of said latch to its unlocking position.
The present invention also relates to a fitted nacelle a thrust reverser according to the above.
Other features and advantages of the present invention will appear on reading the description which will follow, and on the examination of figures appended hereto, in which:
FIG. 1 schematically represents an inverter twin doors in a direct jet configuration, FIG. 2 represents this inverter in jet configuration inverted, - Figure 3 shows an overview of two doors binoculars fitted with a locking system conforming to a first embodiment of the invention, FIGS. 4 to 10 show this locking system in its different operating positions, FIG. 11 is a block diagram of the actuating circuit of four twin doors of a thrust reverser, a device in accordance with the above being disposed between the doors of each pair of twin doors,

5 - the Figures 12 to 15 illustrate a second locking system according to the invention, in its different positions of operation, FIGS. 16a, 16b, 16c, 16d illustrate a third mode of embodiment of the locking system according to the invention, represented from different angles, FIGS. 17a to 17d, 18a to 18d, 19a to 19d, and 20a to 20c.
illustrate this same locking system in its different operating positions, FIGS. 21a, 21b, 21c illustrate a fourth mode of embodiment of the locking system according to the invention, represented according to different angles of view, - Figures 22a, 22b, 22c; 23a, 23b, 23c; 24a, 24b, 24c and 25a, 25b, 25c illustrate this locking system in its different operating positions, FIG. 26 is a figure similar to FIG. 3, illustrating a fifth embodiment of a locking system according to the invention, FIG. 27 represents this locking system in its part which is in the upstream gate, and FIGS. 28 to 33 show this locking system in the area which is in the downstream part, in different operating positions.
On all these figures, identical references or analogues designate organs or groups of identical or like.
Referring to Figure 1, on which we can see a structure fixed internal nacelle, intended to streamline an aircraft turbojet engine (no shown).
The axis A of this turbojet engine is indicated in dashed lines in FIGS.
and 2, the upstream portion of this turbojet engine to the left of the figures, and the downstream part on the right of these figures.

6 As is known per se, the fixed internal structure 1 can technically be formed of composite material, and may have sound absorption characteristics to minimize noise caused by the circulation of the cold air flow in the cold air vein 3.
This cold air stream 3, substantially annular, is defined by a part by the internal fixed structure 1, and secondly by the part peripheral of the nacelle, conventionally comprising a thrust reverser device 5.
As is known per se, such a device for inverting thrust is movable between the configuration visible in Figure 1, called jet direct, in which the flow of cold air D circulates inside the vein 3 of upstream downstream of the nacelle, and the visible configuration of FIG.
jet reversed in which the flow of cold air I is rejected upstream of the nacelle, so as to exert a counter-thrust force.
The direct jet configuration corresponds to the situations of take off and cruise flight from the aircraft, and the jet situation inverted corresponds to the landing situation of the aircraft, in which look for minimize the braking distance.
More particularly, in the context of the present invention, the thrust reverser device 5 is of the type with twin doors.
This means that the deflection of the cold air flow upstream of the nacelle is obtained by means of two doors, upstream respectively 7 and downstream 9, articulated about respective axes of rotation 12 and 13.
It must of course be understood that several pairs of such twin doors can be provided on the periphery of the nacelle, only one however, such pair is shown in the accompanying figures in a worry simplification.
The upstream door 7 extends between the front frame 15, which is a part fixed of the nacelle, and the downstream door 9.
This downstream door 9 extends between the upstream door 7 and the rear edge 17 of the nacelle.
In the configuration of FIG. 1, the two doors 7 and 9 are closed, thus forcing the flow of cold air D driven by the fan of the turbojet (not shown) to circulate inside the air vein cold 3, thus ensuring the thrust necessary for the propulsion of the aircraft (configuration direct jet).

7 It should be noted that the downstream door 9 has on its edge upstream, a skin that advances to the outer downstream edge of the door upstream 7, thus ensuring the aerodynamic continuity of the outside of the nacelle.
When we want to reverse the thrust of the basket, and therefore to go into reverse jet configuration, we open the two doors 7 and 9 in them pivoting about their respective axes 11 and 13 so as to bring to their position visible in Figure 2.
In this configuration, a part 11 of the cold air flow flowing through the interior of the vein 3 is deflected upstream of the nacelle by the door upstream 7.
Another part 12 of the cold air flow passes between the downstream edge 23 of the upstream door 7 and the fixed internal structure 1 of the nacelle 1, and then deflected by the downstream door 9 which completely closes the cold air vein 3.
In what follows, we will describe a locking system of upstream and downstream doors 9 which is in the zone Z indicated in FIG.
To make this description, one will use the directions of a XYZ trihedron, in which the X direction is substantially parallel to the A axis of the nacelle, Y is substantially parallel to the hinge pins 11, 13 of the doors upstream 7 and downstream 9, and Z is perpendicular to the X and Y directions.
Referring to Figure 3, we can see that the system of lock 25 according to the invention comprises a hook 27 pivotally mounted on the upstream door 7 about a Z direction axis.
A locking latch 29 is itself pivotally mounted on the door upstream 7 about another direction axis Z.
This locking latch 29 has a shank 31 terminated by a roller 33, this tail itself being capable of cooperating with a tail hook 27, so as to prevent the rotation of the latter.
The latch 29 further comprises a head 37 likely to be 30 pushed by a slider 39, slidably mounted on the underside of the door upstream 7, and connected by a hinge 40 to the end of the rod 41 of a jack hydraulic or electrical 43, which cylinder can pass the door uphill 7 from its closed position (direct jet ¨ Figure 1) to its open position ( jet inverted ¨ figure 2).

8 Note that the downstream door 9 is connected to the upstream door 7 by a pair of connecting rods 45a, 45b, arranged so that the opening / closing of the upstream door causes the opening / closing of the downstream door 9.
The hook 27 cooperates with a pin 47 extending substantially in the direction Z, integral with the sliding cowl, preferably surrounded a roller 49.
Spiral springs 51, 53, respectively centered on the axes rotation of hook 27 and latch 29, tend to rotate respectively these two bodies in clockwise and anti-clockwise directions.
Belleville washers 54a, 54b provide elasticity and a damping movement of the slide 39 relative to the upstream gate 7. Without action of the jack 41 on the slider 39, the springs 54a and 54b are advantageously adjusted so that the spring 54b keeps the slider 39 away of the roller 37, in order to preserve the lock in case of rupture of a jack 41.
The operating mode of the locking system that comes to be described will now be explained in the light of FIGS. 4 to 10.
When in a direct jet configuration, the hook 27 is closed on the pin 47, as can be seen in FIG. 4, the tail 31 of the latch 29 prevents any rotation of this hook 27, and therefore any opening untimely upstream and downstream doors 9. It should be noted that there is no contact between the slicer 39 and the roller 37 of the latch 29.
When one wishes to go into reverse jet configuration (figure 2), the actuator 43 is actuated so that its stem 41 extends, and causes thus the sliding of the slider 39 with respect to the upstream door 7, to against the elasticity of Belleville washers 54a.
In doing so, as can be seen in Figure 5, the end of slide 39 acts on the head 37 of the latch 29, against the spring spiral 53, so that the tail 31 of this latch 29 releases the tail 35 of the hook 27.
Thus, as can be seen in Figure 6, under the effect of the spring spiral 51, the hook 27 pivots counterclockwise, thus releasing the pawn 47 of the downstream door 9.
Thus, under the effect of the extension of the rod 41 of the jack 43, the two upstream 7 and downstream 9 doors interconnected by the connecting rods 45a and 45b can pivot to their open position shown in Figure 2, allowing of return the cold air flow to the front of the nacelle, and thus achieve the reverse thrust function.

9 When you want to go back to the direct jet position (FIG. 1), the rod 41 of the cylinder 43 is retracted, which has the particular effect of of bring the pin 47 of the downstream gate 9 to the inside of the hook 27 (see FIG.
7).
In doing so, the pin 47 ends up against the hook 27 and makes rotate it clockwise against the spiral spring (Figures 8 and 9), until the tail 35 of the hook 27 passes the tail 31 latch 29, allowing the return of this latch in its initial position (Figure

10): we find ourselves in the configuration where this hook 27 blocks all relative movement of the upstream and downstream doors 9, 9 thus achieving a locking security completely independent of other locking systems.
Referring to Figure 11, one can see in a synthetic way the actuating and locking circuits of four twin doors a same thrust reverser, equipped in particular with a system of locking as the one just described.
As can be seen in this FIG. 11, each upstream door 7a, 7b, 7c, 7d is actuated by a respective cylinder 43a, 43b, 43c, 43d, which is capable of acting on a respective locking system 25a, 25b, 25c, 25d, disposed between the upstream doors 7a, 7b, 7c, 7d and downstream 9a, 9b, 9c, 9d, according to the explanation just given.
As mentioned above, these systems of 25a, 25b, 25c, 25d are independent of two other systems of locking, to guard against unintentional opening of twin doors.
For each pair of twin doors, there is indeed on the one hand a so-called primary locking system VPa, VPb, VPc, VPd, acting directly on the upstream doors 7a, 7b, 7c, 7d, controlled by a unit of specific control PLCU (Primary Lock Control Unit: control unit primary locks).
In addition, synchronization locks VSa and VSb are disposed between two adjacent upstream gates, on the one hand 7a, 7b and on the other hand 7c, 7d, preventing the opening of an upstream door as its upstream door adjacent is not itself open: such a system is known per se patent FR 2 823 259, it will therefore not be described further in details here.
As can be seen in Figure 11, the ADCU control unit (Actuator Directional Control Unit: actuator control unit) jacks 43a, 43b, 43c, 43d, is totally independent of the unit of PLCU control, so the three locking systems that come to be described (25, VP, VS) are totally independent of each other, guaranteeing the perfect security of the door locks inverter 5 thrust in direct jet position.
Note also that the different axial positions of these three locking systems provide maximum security vis-à-vis accidents that may occur inside the nacelle, such as a break of motor disk (rotor burst).
Referring now to FIGS. 12 to 15, on which shown another embodiment of the locking system according to the invention.
As we can understand by seeing the XYZ axis system shown in these figures, the pivoting hook 27 and latch 29 is now performed around axes parallel to the Y direction.
In other words, in the present embodiment, the rotation hook 27 and latch 29 is performed around substantially parallel axes to the axes of rotation 11 and 13 of the upstream and downstream doors 9 and 9, while in the previous embodiment, the axes of rotation of the hook 27 and the latch 29 were substantially perpendicular to the axes of rotation 11 and 13 of the doors 7 and 9, and the axis A of the nacelle.
As in the previous embodiment, an extension 41 of the cylinder rod 43 has the effect of pushing on the head 37 of the latch 29, to against the spiral spring 53, thus causing rotation on the latch in clockwise and releasing by the same the tail 35 of the hook 27, which can then pivot under the action of the spiral spring 51 in the counterclockwise direction, thus releasing the pin 47 secured to the downstream door 9 (see FIGS.
13).
When the rod 41 of the cylinder 43 retracts, it therefore causes the closing the downstream door 9 on the upstream door 7 by means of the rods 45a, and 45b, and the pin 47 is relocated inside the hook thus causing the latter to pivot in a clockwise direction against of spiral spring 51, until the tail 35 of this hook overrides the tail 31 of this latch 29 (see Figures 14 and 15), thereby blocking at again the pin 47 in a position corresponding to the jet configuration from the basket.

11 The embodiment of Figures 16 to 20 differs from the two previous, in that the hook 27 is now pivotally mounted on the door upstream 7 about an axis substantially parallel to the axis A of the nacelle, the latch 29 being in turn disposed substantially as in the first mode embodiment described above.
As part of this particular arrangement, the tail 35 of the hook 27 extends in a direction substantially parallel to the median plane of this hook, that is to say in a direction substantially parallel to the axis AT
of the nacelle (X direction).
As in the two previous embodiments, the thrust exerted by the slider 39 on the head 37 of the latch 29, when the extension of the rod 41 of the cylinder 43, has the effect of clearing the tail 31 of the latch 29 of that 35 of the hook 47 (see FIGS. 16 and 17), thus releasing the pawn 47, thereby allowing the opening of the two twin doors 7 and 9.
When the rod 41 of the cylinder 43 retracts (see FIG. 18), the two twin doors 7 and 9 close, bringing the pin 47 into contact with the hook 27 that rotates clockwise against the effort practiced by the spiral spring 51, until the tail 35 of this hook 27 cross the tail 31 of the latch 29 (see FIG. 19), thus ensuring locking the two upstream doors 7 and downstream 9 relative to each other.
Referring now to Figures 20 to 26, on which represented yet another embodiment of the locking system according to the invention.
As can be seen, in this embodiment, provision is made for a bolt 27 slidably mounted inside the upstream door 7, against a coil spring 51.
The movements of the bolt 27 are carried out substantially according to the direction X, that is to say parallel to the axis A of the nacelle.
This bolt 27 is likely to move against the spring helical 51 under the action of the tail 31 latch 29, when it is clockwise by the slider 39 mounted at the end of the rod 41 of the cylinder 43. This tail 31 may advantageously have a stirrup shape to surround the bolt 27.
The configuration of FIGS. 20a, 20b, 20c corresponds to the direct jet configuration, in which it is desired that the doors upstream 7 and downstream 9 are locked relative to each other.

12 In this configuration, the spring 51 is in complete extension, so that the downstream end of the bolt 27 protrudes from the downstream edge of the door 7, and penetrates a keeper 61 (that is to say in a corresponding hole) formed on the upstream edge of the door 9.
In this way, the bolt 27, which works in shear, prevents any relative movement of the upstream edge of the downstream gate 9 with respect to the downstream edge of the upstream door 7.
When you want to open doors binoculars, it acts on the cylinder 43 so as to proceed with the extension of her rod 41, which has the effect of pivoting the latch 29 in the direction time, and and to translate the bolt 27, so that it compresses the coil spring and thus no longer protrudes from the downstream edge of the upstream door 7, thereby freeing the striker 61, so that the upstream edge of the downstream door 9 is no longer locked by relative to the downstream edge of the upstream door 7 (see FIGS. 21a, 21b, 21c) and can thus open the two doors (see Figures 22a, 22b, 22c).
During this opening, a stirrup 63, pivotally mounted around a axis substantially parallel to the axes of rotation 11 and 13 of the upstream doors 7 and downstream 9, tilts around its axis under the action of a spiral spring 65 until it prevents the bolt 27 from coming out of the downstream edge of the door upstream 7.
When it is desired to close the two doors 7 and 9 of the inverter of pushing, the rod 41 of the cylinder 43 is retracted, as can be seen on FIG.
FIG. 23, which has the effect of bringing the downstream door 9 back to a position or it presses, via a support member 67, on the stirrup 63 (see in particular FIGS. 24b and 24c), thus causing the pivoting of this stirrup 63 at against its spiral spring 55, and this, until the bolt 27 is released and lodges again inside the striker 61, under the action of its spring helical 51, as can be seen in particular in FIGS. 25a, 25b and 25c.
When the bolt 27 has regained this position, it ensures again the relative blocking of upstream and downstream doors 9 and 9, and therefore the perfect maintenance of the thrust reverser in its direct jet configuration (see Figure 1).
Referring now to Figures 26 to 34, on which represented yet another embodiment of the locking system according to the invention.

13 This embodiment differs from the first three modes of previously described in that the pin 47 is now mounted on the fixed structure of the thrust reverser, in the vicinity of the downstream edge of the downstream door 9.
The hook 27 is in turn mounted on the downstream door 9, at the right of the pin 47, pivoting on an axis substantially parallel to the axes 11 and 13 of the two doors.
Like this and visible in Figure 27, a first latch 290 is pivotally mounted on the downstream flap 9, about an axis substantially parallel to the rotation axes of the two upstream and downstream doors 7 and 9.
The head 370 of this first latch 290 is likely to be actuated by the slider 39 mounted at the end of the rod 41 of the cylinder 43.
The tail 310 of this first latch 290 cooperates with a cable 69 slidably mounted relative to the downstream door 9, and extending to a second latch 29, pivotally mounted about an axis substantially parallel to the axes 11 and 13 of the downstream door 9, against a spiral spring 53.
The head 37 of this latch 29 cooperates with the cable 69, and the tail 31 of this latch 29 cooperates with a tail 35 of the hook 27, so similar to what has been discussed for the previous embodiments.
More specifically, in the locking position of the two doors 7 and 9, the slider 39 exerts no effort on the head 370 of the first latch so that the tail 31 of the second latch 29 blocks the tail 35 of the lock 27, preventing the latter from pivoting, and thus to disengage from the pin 47 integral with the fixed structure of the nacelle: the downstream door 9, and thereby the upstream door 7 (by means of connecting rods 45a and 45b) can not is open.
Figures 29 show the hook 27 abutting the pawn 47, during an attempt to unintentional opening.
When it is desired to open the upstream doors 7 and downstream 9, we proceed to the extension of the rod 41 of the cylinder 43, which has for effect of move the slider 39 which rotates the first latch 290 in the counterclockwise direction.
In doing so, a traction force is exerted on the cable 69 by the tail 310 of this latch 290.
This pulling force has the effect of rotating the second latch 29 in a clockwise direction, and thus release the tail 35 of the

14 hook 27, as can be seen in Figure 30. Under the effect of the spring spiral 51, the hook 27 then pivots counterclockwise, thus releasing the pawn 47 integral with the fixed structure of the thrust reverser (see Figure 31):
both doors 7 and 9 can then open.
When you want to close these two doors, you retract the rod 41 of the cylinder 43, which has the effect of bringing the hook 7 in contact with the pawn 47 (see Figure 32) and thus to rotate this hook 27 against the spring 51 until the tail 35 of this hook crosses the tail 31 of the second latch 29 and is thus in the locking position shown in FIG. 33, in which the two doors 7 and 9 are perfectly immobilized.
As can be understood in the light of the description which precedes, the present invention provides a locking system for both twin doors which is totally independent of the other systems of locking (primary locking and synchronized locking), without is necessary to provide no additional specific control means.
As will be understood from the description which preceding, and in particular to the examination of Figure 11, only primary locks VPa, VPb, VPc, VPd are controlled by the PLCU unit, the other locks 25a, 25b, 25c, 25d and VSa, VSb being actuated by the simple fact of the moving the twin doors by the cylinders 43a, 43b, 43c, 43d.
So, for a thrust reverser with four pairs of twin doors as shown in fig 11, only four VPa locks, VPb, VPc, VPd require control means, which is extremely advantageous in terms of weight, cost and ease of maintenance.
Of course, the present invention is not limited to described and illustrated embodiments provided as simple examples.

Claims (10)

1. thrust reverser for an aircraft turbojet engine nacelle, comprising:
at least one pair of twin doors comprising a door upstream (7), a downstream door (9) connected by at least one connecting rod (45a, 45b) at the upstream door (7), and at least one actuating cylinder (43) of the upstream door (7), between a direct jet position in which these two doors are closed, and an inverted jet position in which these two doors are open and able to deflect at least one part (I) of the cold air flow likely to circulate inside the the nacelle, and means (25) for locking / unlocking said doors upstream and downstream between them under the sole action of said cylinder (43). The thrust reverser according to claim 1, wherein said locking / unlocking means comprise:
a hook (27) pivotally mounted on said upstream door (7), between a locking position of a pin (47) integral with said downstream door (9), and an unlocking position of this pin (47), - Elastic return means (51) of said hook to its lock position, a latch (29) pivotally mounted on said upstream door (7) between a locking position in which it holds said hook (27) in its locking position, and an unlocking position, in which it authorizes the passage of said hook (27) from its locking position at its unlocking position, resilient return means (53) of said latch (29) towards its blocking position, said jack (43) and said latch (29) being arranged with respect to the other so that an extension of said cylinder (43) rotates said latch (29) towards its unlocking position. 3. Thrust reverser according to claim 2, wherein said hook (27) and said latch (29) are pivotally mounted about axes substantially perpendicular to the axes of rotation (11, 13) of the upstream doors (7) and downstream (9) and to the axis (A) of the nacelle. The thrust reverser of claim 2, wherein said hook (27) and said latch (29) are pivotally mounted about axes substantially parallel to the axes of rotation (11) of the upstream (7) and downstream gates (9). A thrust reverser according to claim 2, wherein said hook (27) is pivotally mounted about an axis substantially parallel to the axis (A) of the nacelle, and said latch (29) is pivotally mounted about an axis substantially perpendicular to the axes of rotation (11, 13) of the upstream doors (7) and downstream (9) and to the axis (A) of the nacelle. The thrust reverser of claim 1, wherein said locking / unlocking means comprise:
a bolt (27) slidably mounted in said upstream door (7), between a latching position of a striker (61) formed in said downstream door (9), and an unlock position of this lock (61) resilient return means (51) of said bolt (27) towards its lock position, a latch (29) pivotally mounted on said upstream door (7) and cooperating with said bolt (27) so that a rotation of this latch (29) has the effect of sliding the bolt (27), said jack (43) and said trigger (29) being arranged one by relative to the other so that an extension of said cylinder (43) pivoting said latch (29) in a direction causing the sliding said bolt (27) to its unlocking position. The thrust reverser according to claim 6, wherein said locking / unlocking means further comprise a caliper (63) pivotally mounted on said upstream door (7) about an axis substantially parallel to the axes of rotation (11, 13) of said upstream (7) and downstream (9) gates, and elastic means (65) reminding this stirrup to a position in which it ensures the maintenance of said bolt (27) in its unlocking position. The thrust reverser of claim 7, wherein said downstream door (9) comprises a support member (67), able to rotate said stirrup (63) against said resilient means (65). The thrust reverser according to claim 1, wherein said locking / unlocking means comprise:
a hook (27) pivotally mounted on said downstream door (9), between a locking position of a pin (47) integral with the structure fixed of said inverter, and an unlocking position of this counter (47) resilient return means (51) of said hook (27) towards its lock position, a latch (29) pivotally mounted on said downstream door (7) between a locking position in which it holds said hook (27) in its locking position, and an unlocking position, in which it authorizes the passage of said hook (27) from its locking position at its unlocking position, resilient return means (53) of said latch (29) towards its blocking position, a cable (69) one end of which is slidably mounted on said upstream door (7), and whose other end is connected to said latch (29), so that an extension of said jack (43) causes the sliding said cable (69) with respect to said upstream gate (7), and thus the rotation of said latch (29) towards its position of release. 10. Nacelle equipped with a thrust reverser according to one any of the preceding claims.